Turbine engine comprising a steam system

Abstract

A turbine engine for an aircraft includes a turbocharged engine having a core air flow path, having a fan shaft coupled to the turbocharged engine to rotate the fan shaft, and a steam system. A combustor is located in the core air flow path for combusting a fuel and generating a combustion gas. The steam system extracts water from the combustion gas and vaporizes the water to produce steam. A steam system is fluidly coupled to the core air flow path to inject steam into the core air flow path. The steam system includes a controller configured to determine a moisture content of the core air upstream of the steam injection location and to vary a position of the steam flow control valve to control a flow of steam into the core air flow path.

Description

Technical Field

[0001] The present disclosure generally relates to turbine engines including steam systems. Background Art

[0002] Turbine engines used in aircraft generally include a fan and a core section arranged in flow communication with each other. A combustor is arranged in the core section to generate combustion gases for driving a turbine in the core section of the turbine engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0003] Features and advantages of the present disclosure will be apparent from the following description of various exemplary embodiments as illustrated in the accompanying drawings, wherein like reference numbers generally indicate identical, functionally similar, and / or structurally similar elements.

[0004] Figure 1 is a schematic cross-sectional view of a turbine engine including a steam system according to the present disclosure, taken along a longitudinal centerline axis of the turbine engine.

[0005] Figure 2 According to the present disclosure Figure 1 Schematic diagram of the turbine engine and steam system.

[0006] Figure 3 is a schematic diagram of a turbine engine and steam system according to an embodiment of the present disclosure.

[0007] Figure 4 is a schematic diagram of a turbine engine and steam system according to an embodiment of the present disclosure.

[0008] Figure 5 It shows the control Figures 2 to 4 A flow chart of a method for a steam system as shown in any one of the Figures. DETAILED DESCRIPTION

[0009] Features, advantages and embodiments of the present disclosure are set forth or apparent through consideration of the following detailed description, drawings and claims.In addition, the following detailed description is exemplary and is intended to provide further explanation without limiting the scope of the present disclosure as claimed.

[0010] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0011] As used herein, the terms "first," "second," and the like may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0012] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle and refer to the normal operating attitude of the gas turbine engine or vehicle. For example, for a gas turbine engine, front refers to a position closer to the engine inlet, while rear refers to a position closer to the engine nozzle or exhaust.

[0013] The terms "upstream" and "downstream" refer to relative directions with respect to the flow of a fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction to which the fluid is flowing.

[0014] The terms “coupled,” “fixed,” “attached,” “connected,” and the like refer to both direct coupling, fixing, attachment, or connection as well as indirect coupling, fixing, attachment, or connection through one or more intermediate components or features, unless otherwise specified herein.

[0015] As used herein, the terms "axial" and "axially" refer to directions and orientations extending substantially parallel to the centerline of the turbine engine. Additionally, the terms "radial" and "radially" refer to directions and orientations extending substantially perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations extending in an arc around the centerline of the turbine engine.

[0016] When discussed in the context of radial directions, references to "inner" and "outer" refer to positions relative to the longitudinal centerline of the component.

[0017] As used herein, a "bypass ratio" of a turbine engine is the ratio of bypass air passing through a bypass of the turbine engine to core air passing through a core inlet of a turbo-engine of the turbine engine.

[0018] As used herein, the "compression ratio" of a compressor is the ratio of the compressor outlet pressure at the outlet of the compressor to the compressor inlet pressure at the inlet of the compressor. The compressor outlet pressure and the compressor inlet pressure are measured as static air pressures perpendicular to the direction of core air flow through the compressor.

[0019] As used herein, the "pressure expansion ratio" of a turbine is the ratio of the pressure at the inlet of the turbine to the pressure at the outlet of the turbine.

[0020] As used herein, a "core air flow path zone" is an area or region of the core air flow path where the core air flowing through the core air flow path has different or distinct thermodynamic properties than surrounding or adjacent areas of the core air flow path.

[0021] The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise.

[0022] Here and throughout the specification and claims, range limitations are combined and interchanged. Unless the context or language indicates otherwise, these ranges are identified and include all subranges contained therein. For example, all ranges disclosed herein include the endpoints, and the endpoints can be combined independently of each other.

[0023] As described above, the burner is arranged in the core section of the turbine engine to produce combustion gases for driving the turbine in the core section. The energy and heat generated by the burner are not all used to drive the turbine of the turbine section. Instead, some waste heat is discharged through the jet exhaust nozzle section in a conventional turbine engine. The turbine engine discussed herein includes a steam system for recovering some energy from waste heat by generating steam and driving a steam turbine. After flowing through the steam turbine, the steam can be injected into the core air flow path, and more specifically, injected into the burner. Although some steam flowing through the main combustion zone of the burner is beneficial, steam with a mass flow rate greater than, for example, ten percent (10%) or fifteen percent (15%) of water to air ratio may cause flame stability problems and flame dynamics problems during fuel combustion, particularly for highly reactive fuels such as diatomic hydrogen. For example, when an aircraft (turbine engine) is operated under humid atmospheric conditions (such as rain, hail, or clouds), the air flowing into the turbine engine and therefore the core air flowing into the core air flow path contains moisture. Thus, the amount of steam injected into the core air through the steam system may be controlled based on the moisture content of the incoming core air, and the amount of steam injected into the core air through the steam system may be reduced when the turbine engine is operating in humid atmospheric conditions compared to other atmospheric conditions with lower moisture content.

[0024] Instead, as discussed herein, steam can be injected into the core air flow path at multiple locations, with a portion of the steam flowing through the primary combustion zone. In this way, the water-to-air ratio of the primary air flowing through the primary combustion zone can be maintained at a sufficiently low level to achieve good flame performance.

[0025] Now referring to the accompanying drawings, Figure 1 is a schematic cross-sectional view of a turbine engine 10 including a steam system 100 taken along a longitudinal centerline axis 12 (provided for reference) of the turbine engine 10 in accordance with an embodiment of the present disclosure. Figure 1 As shown, the turbine engine 10 has an axial direction A (extending parallel to the longitudinal centerline axis 12 ) and a radial direction R orthogonal to the axial direction A. Generally, the turbine engine 10 includes a fan section 14 and a turbocharger engine 16 disposed downstream of the fan section 14 .

[0026] The turbocharger engine 16 includes an outer casing 18 that is substantially tubular and defines an annular core inlet 20. Figure 1 As schematically shown in FIG. 1 , outer casing 18 encloses, in series flow relationship, a compressor section 21 including a supercharger or low pressure compressor (LPC) 22 followed downstream by a high pressure compressor (HPC) 24; a combustor 26; a turbine section 27 including a high pressure turbine (HPT) 28 followed downstream by a low pressure turbine (LPT) 30; and one or more core exhaust nozzles 32. A high pressure (HP) shaft 34 or spool drivingly connects the HPT 28 to the HPC 24 so that the HPT 28 and the HPC 24 rotate in unison. The HPT 28 is drivingly coupled to the HP shaft 34 so that the HP shaft 34 rotates when the HPT 28 rotates. A low pressure (LP) shaft 36 drivingly connects the LPT 30 to the LPC 22 so that the LPT 30 and the LPC 22 rotate in unison. LPT 30 is drivingly coupled to LP shaft 36 to rotate LP shaft 36 when LPT 30 rotates. Compressor section 21 , combustor 26 , turbine section 27 , and one or more core exhaust nozzles 32 together define a core air flow path 33 .

[0027] for Figure 1 In the embodiment shown in FIG. 1 , the fan section 14 includes a fan 38 (eg, a variable pitch fan) having a plurality of fan blades 40 coupled to a disk 42 in a spaced-apart manner. Figure 1 As shown, fan blades 40 generally extend outwardly from disk 42 in a radial direction R. Each fan blade 40 is rotatable relative to disk 42 about pitch axis P by virtue of fan blades 40 being operably coupled to actuator 44, which is configured to collectively and uniformly change the pitch of fan blades 40. Fan blades 40, disk 42, and actuator 44 together are rotatable about longitudinal centerline axis 12 via fan shaft 45, which is powered by LP shaft 36 across a power gearbox (also referred to as gearbox assembly 46). Gearbox assembly 46 is Figure 1 The gearbox assembly 46 includes a plurality of gears for adjusting the rotational speed of the fan shaft 45 , thereby adjusting the rotational speed of the fan 38 relative to the LP shaft 36 .

[0028] Still reference Figure 1In an exemplary embodiment of the present invention, the disk 42 is covered by a rotatable fan hub 48 having an aerodynamic profile to facilitate airflow through the plurality of fan blades 40. In addition, the fan section 14 includes an annular fan casing or nacelle 50 that circumferentially surrounds the fan 38 and / or at least a portion of the turbocharger engine 16. The nacelle 50 is supported relative to the turbocharger engine 16 by a plurality of circumferentially spaced outlet guide vanes 52. In addition, a downstream section 54 of the nacelle 50 extends over an outer portion of the turbocharger engine 16 to define a bypass airflow passage 56 therebetween. One or more core exhaust nozzles 32 may extend through the nacelle 50 and be formed therein. In this embodiment, the one or more core exhaust nozzles 32 include one or more discrete nozzles that are circumferentially spaced around the nacelle 50. Other arrangements of the core exhaust nozzles 32 may also be employed, including, for example, a single core exhaust nozzle that is annular or partially annular around the nacelle 50.

[0029] During operation of the turbine engine 10, a volume of air 58 enters the turbine engine 10 through the engine inlet 60 of the nacelle 50 and / or the fan section 14. The engine inlet 60 may also be referred to as a fan inlet. As the volume of air 58 passes through the fan blades 40, a first portion of the air (bypass air 62) is directed or directed into the bypass airflow passage 56, while a second portion of the air (core air 64) is directed or directed into the upstream section of the core air flow path 33, or more specifically, directed or directed into the core inlet 20. The ratio between the first portion of air (bypass air 62) and the second portion of air (core air 64) is generally referred to as a bypass ratio. In some embodiments, the bypass ratio is greater than 18:1, which is achieved by the steam system 100, which will be further described below. The LPC 22 then increases the pressure of the core air 64, producing compressed air 65, and the compressed air 65 is directed through the HPC 24 and further compressed before being directed into the combustor 26, where the compressed air 65 is mixed with a fuel 67 and combusted to produce combustion gases 66 (combustion products). One or more stages may be used in each of the LPC 22 and the HPC 24, wherein each subsequent stage further compresses the compressed air 65. The compression ratio of the HPC 24 is greater than 20:1, for example, in the range of 20:1 to 40:1. The compression ratio is the ratio of the pressure of the last stage of the HPC 24 to the pressure of the first stage of the HPC 24. The steam system 100 may achieve a compression ratio greater than 20:1, as described in further detail below.

[0030] As described above, the fuel 67 is injected into the combustor 26 using a fuel nozzle, and more specifically, into the combustion chamber (not shown) of the combustor 26. The fuel nozzle can be part of a swirler / fuel nozzle assembly (mixer assembly). As described above, the compressor section 21 including the HPC 24 pressurizes the air, and the combustor 26 receives an annular flow of the pressurized air from the discharge outlet of the HPC 24. The mixer assembly can include a plurality of swirler vanes as part of the swirler, which is used to swirl the compressed air received from the HPC 24 (referred to herein as the main air flowing through the mixer assembly) and generate turbulence in the compressed air. The fuel nozzle injects the fuel 67 into the turbulent airflow of the main air, and the turbulence promotes rapid mixing of the fuel 67 with the main air, producing a fuel-air mixture. The fuel-air mixture is provided from the mixer assembly to the combustor for combustion. Ignition of the fuel-air mixture is accomplished by an igniter (not shown), and the resulting combustion gases 66 flow in the axial direction A of the turbine engine 10 toward and into the annular turbine nozzle of the HPT 28. Most of the fuel 67 injected through the mixer assembly burns in a primary combustion zone in the combustion chamber in an area immediately downstream of the mixer assembly. The turbine nozzle is defined by an annular flow passage that includes a plurality of radially extending, circumferentially spaced HPT stator vanes 68 ( Figure 1 ), these stator blades rotate the gas, causing the gas to flow at an angle and hit the HPT rotor blades 70 ( Figure 1 ). The HPT 28 includes a rotor having a plurality of HPT rotor blades 70. The HPT rotor blades 70 are circumferentially spaced apart, and the HPT stator vanes 68 are located upstream of the HPT rotor blades 70. The rotor may be, for example, a disk or blisk drivingly connected to the HP shaft 34.

[0031] The combustion gases 66 are directed into and expanded through the HPT 28, wherein a portion of the thermal and / or kinetic energy from the combustion gases 66 is extracted via sequential stages of HPT stator blades 68 coupled to the outer casing 18 and HPT rotor blades 70 coupled to the HP shaft 34, thereby causing the HP shaft 34 to rotate, thereby supporting the operation of the HPC 24. The combustion gases 66 are then directed into and expanded through the LPT 30. Here, a second portion of the thermal and / or kinetic energy is extracted from the combustion gases 66 via sequential stages of LPT stator blades 72 coupled to the outer casing 18 and LPT rotor blades 74 coupled to the LP shaft 36, thereby causing the LP shaft 36 to rotate, thereby supporting the operation of the LPC 22 and supporting the rotation of the fan 38 via the gearbox assembly 46. One or more stages may be used in each of the HPT 28 and the LPT 30. The compression ratio of the HPC 24 is in the range of 20:1 to 40:1, which results in a pressure expansion ratio of the HPT 28 in the range of 1.5:1 to 4:1, and a pressure expansion ratio of the LPT 30 in the range of 4.5:1 to 28:1.

[0032] The combustion gases 66, after being directed through the steam system 100 (discussed below), are then directed through one or more core exhaust nozzles 32 of the turbocharger engine 16 to provide propulsive thrust. While the core air 64 flows through the core air flow path 33, the bypass air 62 is directed through the bypass airflow passage 56 and then discharged from the fan bypass nozzle 76 of the turbine engine 10, also providing propulsive thrust. The HPT 28, the LPT 30, and the one or more core exhaust nozzles 32 at least partially define a hot gas path 78 for directing the combustion gases 66 through the turbocharger engine 16.

[0033] As described above, compressed air 65 (core air 64) is mixed with fuel 67 in combustor 26 to form a fuel and air mixture and combusted to produce combustion gases 66 (combustion products). Fuel 67 may include any type of fuel for turbine engines, such as sustainable aviation fuel (SAF), including biofuel, JetA or other hydrocarbon fuels. Fuel 67 may also be a hydrogen-based fuel (H 2 ), although hydrogen-based fuels may include mixtures with hydrocarbon fuels, the fuel 67 used herein is unmixed and is referred to herein as hydrogen fuel. In some embodiments, the hydrogen fuel may include substantially pure hydrogen molecules (i.e., diatomic hydrogen). The fuel 67 may also be a cryogenic fuel. For example, when hydrogen fuel is used, the hydrogen fuel may be stored in a liquid phase at low temperatures.

[0034] Turbine engine 10 includes a fuel system 80 for providing fuel 67 to combustor 26. Fuel system 80 includes a fuel tank 82 for storing fuel 67 therein and a fuel delivery assembly 84. Fuel tank 82 may be located on an aircraft (not shown) to which turbine engine 10 is attached. Figure 1 8, but the fuel system 80 may include any number of fuel tanks 82 as desired. The fuel delivery assembly 84 delivers the fuel 67 from the fuel tank 82 to the combustor 26. The fuel delivery assembly 84 includes one or more lines, conduits, pipes, tubes, etc. configured to deliver the fuel 67 from the fuel tank 82 to the combustor 26. The fuel delivery assembly 84 also includes a pump 86 to direct the flow of the fuel 67 through the fuel delivery assembly 84 to the combustor 26. In this way, the pump 86 pumps the fuel 67 from the fuel tank 82 through the fuel delivery assembly 84 and into the combustor 26. The fuel system 80, and more specifically, the fuel tank 82 and the fuel delivery assembly 84, whether together or separately, can be a fuel source for the combustor 26.

[0035] In some embodiments, for example, when the fuel 67 is a hydrogen fuel, the fuel system 80 includes one or more vaporizers 88 (illustrated by dashed lines) and a metering valve 90 (illustrated by dashed lines) in fluid communication with the fuel delivery assembly 84. In this example, the hydrogen fuel is stored in the fuel tank 82 as a liquid hydrogen fuel. The one or more vaporizers 88 heat the liquid hydrogen fuel flowing through the fuel delivery assembly 84. The one or more vaporizers 88 are positioned in the flow path of the fuel 67 between the fuel tank 82 and the combustor 26, and are located downstream of the pump 86. The one or more vaporizers 88 are thermally connected to at least one heat source, such as waste heat from the turbine engine 10 and / or from one or more systems (not shown) of the aircraft. The one or more vaporizers 88 heat the liquid hydrogen fuel, and the liquid hydrogen fuel is converted into gaseous hydrogen fuel in the one or more vaporizers 88. The fuel delivery assembly 84 guides the gaseous hydrogen fuel to the combustor 26.

[0036] A metering valve 90 is positioned downstream of the one or more vaporizers 88 and the pump 86. The metering valve 90 receives the hydrogen fuel in a substantially complete gas phase or in a substantially complete supercritical phase. The metering valve 90 provides a fuel flow to the burner 26 in a desired manner. More specifically, the metering valve 90 provides a desired volume of hydrogen fuel at, for example, a desired flow rate to a fuel manifold that includes one or more fuel injectors that inject the hydrogen fuel into the burner 26. The fuel system 80 may include any components for supplying the fuel 67 from the fuel tank 82 to the burner 26 as needed.

[0037] Turbine engine 10 includes a steam system 100 in fluid communication with one or more core exhaust nozzles 32 and fan bypass nozzles 76. Steam system 100 extracts steam from combustion gases 66 as they flow through steam system 100, as described in further detail below.

[0038] Figure 1 The turbine engine 10 depicted in the drawings is provided as an example only. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the fan 38 may be configured in any other suitable manner (e.g., as a fixed pitch fan) and may also be supported using any other suitable fan frame configuration. In addition, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In other exemplary embodiments, aspects of the present disclosure may be incorporated into any other suitable turbine engine, such as a turbofan engine, a propfan engine, and / or a turboprop engine.

[0039] Figure 2 1 is a schematic diagram of a turbine engine 10 having a steam system 100a according to an embodiment of the present disclosure. For clarity of other steam systems discussed herein, the steam system 100a of this embodiment will be referred to as the first steam system 100a. The first steam system 100a can be used as Figure 1 1. The steam system 100 in the turbine engine 10 is shown in FIG. 1. For clarity, Figure 2 Various features of the turbine engine 10 described and illustrated above are schematically illustrated in FIG. Figure 2 Some components are not shown in FIG. 1 , but the description of these components also applies here. The first steam system 100 a includes a boiler 102 , a condenser 104 , a water separator 106 , a water pump 108 , and a steam turbine 110 .

[0040] The boiler 102 is a heat exchanger that vaporizes liquid water from a water source to produce steam or water vapor, as described in further detail below. Thus, the boiler 102 is a steam source. In particular, the boiler 102 is an exhaust gas-water heat exchanger. The boiler 102 is connected to the hot gas path 78 ( Figure 1 ) and is positioned downstream of the LPT 30. The boiler 102 is also in fluid communication with a water pump 108, as described in further detail below. The boiler 102 may include any type of boiler or heat exchanger for extracting heat from the combustion gases 66 and vaporizing the liquid water into steam or water vapor as the liquid water and the combustion gases 66 flow through the boiler 102.

[0041] The condenser 104 is a heat exchanger that further cools the combustion gases 66 as they flow through the condenser 104, as described in further detail below. In particular, the condenser 104 is an air-exhaust gas heat exchanger. The condenser 104 is in fluid communication with the boiler 102 and is positioned within the bypass air flow passage 56. The condenser 104 may include any type of condenser for condensing water (e.g., in liquid form) from the exhaust (e.g., the combustion gases 66).

[0042] The water separator 106 is in fluid communication with the condenser 104 for receiving the cooled exhaust gas (combustion gases 66) having condensed water entrained therein. The water separator 106 is also in fluid communication with one or more core exhaust nozzles 32 and with a water pump 108. The water separator 106 includes any type of water separator for separating water from the exhaust gas. For example, the water separator 106 may include a cyclone separator that uses vortex separation to separate water from air. In such an embodiment, the water separator 106 generates a cyclonic flow within the water separator 106 to separate water from the cooled exhaust gas. Figure 2 , the water separator 106 is schematically depicted as being located in the nacelle 50, but the water separator 106 may be located elsewhere within the turbine engine 10, for example, radially inward of the nacelle 50, closer to the turbocharger engine 16. The water separator 106 may be driven to rotate by one of the engine shafts (e.g., the HP shaft 34 or the LP shaft 36). As described above, the boiler 102 receives liquid water from a water source to generate steam or water vapor. Figure 2 In the embodiment shown in , the condenser 104 and the water separator 106 , either individually or collectively, are the source of water for the boiler 102 .

[0043] The water pump 108 is in fluid communication with the water separator 106 and with the boiler 102. The water pump 108 is in fluid communication with the condenser 104 via the water separator 106. The water pump 108 can be any suitable pump, such as a centrifugal pump or a positive displacement pump. The water pump 108 directs the separated liquid water 124 through the boiler 102, where the water 124 is converted back into steam. The steam is transported through the steam turbine 110 and then injected into the core air flow path 33, such as into the combustor 26.

[0044] In operation, combustion gases 66 (also referred to as exhaust) flow from the LPT 30 into the boiler 102. The combustion gases 66 transfer heat to water 124 (e.g., in liquid form) within the boiler 102, as described in further detail below. The combustion gases 66 then flow into the condenser 104. The condenser 104 condenses the water 124 (e.g., in liquid form) from the combustion gases 66. The bypass air 62 flows through the bypass airflow passage 56 and flows through or through the condenser 104, and extracts heat from the combustion gases 66, cools the combustion gases 66 and condenses the water 124 from the combustion gases 66 to produce an exhaust-water mixture 120. The bypass air 62 then exits the turbine engine 10 through the fan bypass nozzle 76 to generate thrust, as described in detail above. Therefore, the condenser 104 can be positioned in the bypass airflow passage 56.

[0045] The exhaust-water mixture 120 flows into the water separator 106. The water separator 106 separates water 124 from the exhaust of the exhaust-water mixture 120 to produce separated exhaust gas 122 and water 124. The exhaust gas 122 is discharged from the turbine engine 10 through one or more core exhaust nozzles 32 to produce thrust, as described in detail above. The boiler 102, condenser 104, and water separator 106 thus also define a hot gas path 78 (see Figure 1 ) for directing the combustion gases 66, the exhaust-water mixture 120, and the exhaust gas 122 through the first steam system 100a of the turbine engine 10.

[0046] The water pump 108 passes through one or more water pipelines (such as Figure 2 Water 124 (e.g., in liquid form) is pumped by a duct (as indicated by an arrow pointing to water 124) and flows through the boiler 102. As the water 124 flows through the boiler 102, the combustion gases 66 flowing through the boiler 102 transfer heat to the water 124 to vaporize the water 124 and generate steam 126 (e.g., steam). The steam turbine 110 includes one or more stages of steam turbine blades (not shown) and a steam turbine stator (not shown). The steam 126 is transferred from the boiler 102 through one or more steam lines (e.g., steam turbines). Figure 2 Steam 126 (indicated by arrows in FIG. 1 ) flows into the steam turbine 110 , causing the steam turbine blades of the steam turbine 110 to rotate, generating additional work in an output shaft (eg, one of the engine shafts) connected to the turbine blades of the steam turbine 110 .

[0047] As mentioned above, the turbocharger engine 16 includes a shaft, also referred to as an engine shaft, that couples the various rotating components of the turbocharger engine 16 and other thrust generating components such as the fan 38. Figure 1In the turbocharger engine 16 shown in FIG. 1 , these engine shafts include an HP shaft 34 and an LP shaft 36. A steam turbine 110 is coupled to one of the engine shafts of the turbocharger engine 16, such as the HP shaft 34 or the LP shaft 36. In the illustrated embodiment, the steam turbine 110 is coupled to the LP shaft 36. As steam 126 flows from the boiler 102 through the steam turbine 110, the steam turbine 110 converts the kinetic energy of the gas into mechanical work in the LP shaft 36. The reduced temperature steam (as steam 128) leaving the steam turbine 110 is then injected into the core air flow path 33, such as into the combustor 26, upstream of the combustor 26, or downstream of the combustor 26. The steam 128 flows from the steam turbine 110 through one or more steam lines to the core air flow path 33. The steam 128 injected into the core air flow path 33 adds mass flow to the core air 64, so that less core air 64 is required to produce the same amount of work through the turbine section 27. In this way, the first steam system 100a extracts additional work from heat in the exhaust gases that would otherwise be wasted. The steam 128 injected into the core air flow path 33 is in the range of 20% to 50% of the mass flow through the core air flow path 33 .

[0048] The steam turbine 110 may have a pressure expansion ratio in the range of 2:1 to 6:1. The pressure expansion ratio is the ratio of the pressure at the inlet of the steam turbine 110 to the pressure at the outlet of the steam turbine 110. When the first steam system 100a recovers approximately 70% of the water 124 and converts the water 124 into steam 126, the steam turbine 110 may contribute approximately 25% of the power to the LP shaft 36 (or to the HP shaft 34). The pressure expansion ratio of the steam turbine 110 is in the range of 2:1 to 6:1, the pressure expansion ratio of the LPT 30 is in the range of 4.5:1 to 28:1, and the steam 128 contributes 20% to 50% of the mass flow through the core air flow path 33. The steam turbine 110 expands the steam 126, thereby reducing the energy of the steam 128 leaving the steam turbine 110, and reducing the temperature of the steam 128 to approximately 100% of the compressed air 65 exhausted from the HPC 24 (see Figure 1 ) temperature. This configuration enables the steam 128 to reduce hot spots in the combustor 26 that are created by the combustion of the fuel (e.g., particularly when the fuel is supercritical hydrogen or gaseous hydrogen).

[0049] The steam 128 injected into the core air flow path 33 also enables the HPT 28 to have a greater energy output using fewer stages of the HPT 28 as compared to an HPT without the benefit of the present disclosure. For example, the additional mass flow from the steam 128 through the turbine section 27 helps to produce a greater energy output. As such, due to the higher mass flow (created by the steam injection) leaving the combustor 26, the HPT 28 may have only one stage that can sustainably drive more stages of the HPC 24 (e.g., ten, eleven, or twelve stages of the HPC 24). The steam 128 injected into the core air flow path 33 enables the HPT 28 to have only one stage that drives multiple stages of the HPC 24 without reducing the amount of work produced by the HPT 28 as compared to an HPT without the benefit of the present disclosure, while also reducing the weight of the HPT 28 and improving the efficiency of the HPT 28 as compared to an HPT without the benefit of the present disclosure.

[0050] Due to the added mass flow from steam 126, the required core air 64 (see Figure 1 ) is less, the compression ratio of the HPC 24 can be increased compared to an HPC without the benefit of the present disclosure. As such, the compression ratio of the HPC 24 is greater than 20:1. In some embodiments, the compression ratio of the HPC 24 is in the range of 20:1 to 40:1. Thus, the compression ratio of the HPC 24 is increased, which increases the thermal efficiency of the turbine engine 10 compared to an HPC and a turbine engine without the benefit of the present disclosure. In addition, the HPC 24 can have a reduced throat area due to the added mass flow provided in the turbocharger engine 16 by the steam 126, 128 injected into the turbocharger engine 16. Thus, the HPC 24 has a reduced size (e.g., outer diameter) and reduced weight compared to a turbine engine without the benefit of the present disclosure.

[0051] In some embodiments, the HPC stator blades of at least two stages of the HPC 24 are variable stator blades that are controlled to pitch about a pitch axis to change the pitch of the HPC stator blades. In some embodiments, the HPC 24 includes one or more compressor bleed valves that are controlled to open to bleed a portion of the compressed air 65 from the HPC 24 (see Figure 1 ). One or more compressor bleed valves may be positioned between the fourth stage of the HPC 24 and the last stage of the HPC 24. The HPC stator vanes are variable stator vanes, and the one or more compressor bleed valves help balance the air flow (e.g., compressed air 65) through all stages of the HPC 24. This balance, combined with the steam 128 injected into the core air flow path 33, enables the number of stages of the HPC 24 to include ten to twelve stages to achieve a compression ratio greater than 20:1, such as in the range of 20:1 to 40:1.

[0052] The additional work extracted by the first steam system 100a and the steam 128 injected into the core air flow path 33 enables the turbocharged engine 16 ( Figure 1 ) is reduced in size, which increases the bypass ratio of the turbine engine 10 compared to a turbine engine without the benefit of the present disclosure. As such, the bypass ratio of the turbine engine 10 is greater than 18:1, for example, in the range of 18:1 to 100:1, in the range of 25:1 to 85:1, or in the range of 28:1 to 70:1. As such, the first steam system 100a can achieve an increased bypass ratio compared to a turbine engine without the benefit of the present disclosure, wherein the turbine engine 10 can move a greater amount of air through the bypass, thereby reducing the pressure ratio of the fan 38 and increasing the efficiency of the turbine engine 10.

[0053] Figure 2 The steam system 100 shown in also includes a controller 130. The controller 130 may be a separate, independent controller operable as described herein, or may be another controller of the turbine engine 10, such as an engine controller. The engine controller may be a full authority digital engine control (FADEC). The controller 130 is configured to operate various aspects of the steam system 100a, including the steam control valve 112 in this embodiment. In this embodiment, the controller 130 is a computing device having one or more processors 132 and one or more memories 134. The processor 132 may be any suitable processing device, including but not limited to a microprocessor, a microcontroller, an integrated circuit, a logic device, a programmable logic controller (PLC), an application specific integrated circuit (ASIC) and / or a field programmable gate array (FPGA). The memory 134 may include one or more computer-readable media, including but not limited to non-transient computer-readable media, computer-readable non-volatile media (e.g., flash memory), RAM, ROM, a hard drive, a flash drive, and / or other memory devices.

[0054] The memory 134 may store information accessible to the processor 132, including computer-readable instructions that may be executed by the processor 132. The instructions may be any set of instructions or sequence of instructions that, when executed by the processor 132, cause the processor 132 and the controller 130 to perform operations. In some embodiments, the instructions may be executed by the processor 132 to cause the processor 132 to perform any operations and functions for which the controller 130 is configured, as will be further described below. The instructions may be software written in any suitable programming language, or may be implemented in hardware. Additionally, and / or alternatively, the instructions may be executed in logically and / or virtually independent threads on the processor 132. The memory 134 may also store data that may be accessed by the processor 132.

[0055] The technology discussed herein relates to computer-based systems and actions taken by computer-based systems and information sent to and from computer-based systems. Those of ordinary skill in the art will recognize that the inherent flexibility of computer-based systems allows for various possible configurations, combinations, and divisions of tasks and functions between and among components. For example, the processes discussed herein can be implemented using a single computing device or multiple computing devices working in combination. Databases, memories, instructions, and applications can be implemented on a single system or distributed on multiple systems. Distributed components can operate sequentially or in parallel.

[0056] The turbine engine 10 does not operate under stable operating conditions. On the contrary, the turbine engine 10 operates under various operating conditions. For example, during the normal operating cycle of the aircraft, the turbine engine 10 can operate at high power (e.g., high power operation or condition) when taking off and climbing, and operate (low power operation or condition) with low power (e.g., idle speed) when descending. In this context, high power and low power are relative to each other. During flight, the turbine engine 10 can also operate under cruise, which includes power conditions (operations) between the high power conditions and the low power conditions discussed above. Under different operating conditions, the amount of steam injected into the burner 26 can be adjusted to have less steam, for example, when operating at low power, and more steam when operating at high power.

[0057] The flow of steam 128 into the core air flow path 33 may be controlled, at least in part, by one or more valves. Figure 2 The first steam system 100a shown in FIG. 1 includes one or more flow control valves positioned between the boiler 102 and the burner 26 to control the amount of steam flowing into the core air flow path 33, such as the amount of steam flowing into the burner 26. In this embodiment, the steam control valve 112 is positioned in the flow path (e.g., pipeline) between the steam turbine 110 and the core air flow path 33, such as between the steam turbine 110 and the burner 26. The steam control valve 112 is positioned upstream of the core air flow path 33 and downstream of the steam turbine 110 to control the flow of steam 128 entering the core air flow path 33. Any suitable flow control valve can be used as the steam control valve 112. Such a flow control valve can have a closed position and a plurality of open positions, including a fully open position. The flow control valve can be an electrically operated valve, a hydraulically operated valve, or a pneumatically operated valve. When the flow control valve is hydraulically operated, the hydraulic fluid can be a suitable fluid of the turbine engine 10, including, for example, fuel 67, lubricating oil, etc.

[0058] , the first steam system 100a is fluidly connected to inject steam into the core air flow path 33 at one or more steam injection locations or steam injection zones, thereby adding mass flow to the core air 64, as discussed above. As the core air 64 flows through the core air flow path 33, the thermodynamics of the core air 64 (and the combustion gases 66) change, as discussed above. Therefore, the core air flow path 33 includes a plurality of core air flow path zones. As used herein, a core air flow path zone is a portion (i.e., an area or region) of the core air flow path, wherein the core air 64 has thermodynamic properties that are different or different from those of the surrounding or adjacent areas. For example, when the pressure and temperature of the core air 64 in each of the LPC 22 and the HPC 24 increase, the LPC 22 can be a core air flow path zone, and each of the HPCs 24 can be a core air flow path zone. In addition, the LPC 22 and the HPC 24 can be multi-stage compressors, and each stage of the LPC 22 or the HPC 24 can also be a core air flow path zone. Similarly, the combustor 26, and more specifically, the primary combustion zone within the combustor 26, as discussed below, may be a core air flow path zone. Similar to the LPC 22 and the HPC 24, the HPT 28 and the LPT 30 may be core air flow path zones, and each stage of the HPT 28 and the LPT 30 may be a core air flow path zone. The core air flow path 33 of the turbine engine 10 is annular (i.e., annular about the longitudinal centerline axis 12), and each core air flow path zone may be an annular band of the turbine engine 10, and more specifically, the core air flow path 33. Each steam injection zone corresponds to one of the core air flow path zones.

[0059] exist Figure 2 In the illustrated embodiment, one steam injection zone is depicted, and the depicted steam injection zone is a core air flow path zone of the burner 26, including, for example, a primary combustion zone of the burner 26. For example, the steam 128 may be mixed with the fuel 67 ( Figure 1 ) is injected into the primary air and directly into the primary combustion zone in the mixer assembly, where the steam 128 is mixed with the fuel 67 ( Figure 1 ) combination is injected into the combustor 26. When the fuel 67 is a hydrogen fuel, a combined steam / fuel injector can be used to minimize hot spots in the combustor 26 and control the hydrogen flame.

[0060] The controller 130 can be communicatively and operably coupled to the steam control valve 112 to change the position (i.e., move) of the steam control valve 112 between a plurality of open positions and control the total flow rate of the steam 128 entering the core air flow path 33 (and more specifically, the burner 26). The controller 130 positions the steam control valve 112 in one of the plurality of open positions to provide a desired amount of steam 128 into the core air flow path 33, such as into the burner 26, as shown in FIG. Figure 2 The controller 112 opens the steam flow control valve 112 to increase the amount of steam 128 flowing into the core air flow path 33, and closes (moves to a less open position) the steam flow control valve 112 to reduce the amount of steam 128 flowing into the core air flow path 33. The controller 130 can also completely close the steam flow control valve 112 to cut off the flow of steam 128 into the core air flow path 33.

[0061] As described above, a volume of air 58 flows into the turbine engine 10 through the engine inlet 60, and after flowing through the fan 38, a portion of the volume of air 58 flows into the core air flow path 33 via the core inlet 20 as core air 64. The volume of air 58 is drawn from the air surrounding the turbine engine 10 (ambient air), so the water vapor content (water content) of the ambient air is the initial water content of the core air 64. The controller 130 controls the position of the steam control valve 112, thereby controlling the amount of steam 128 entering the core air flow path 33 to achieve a target water-to-air ratio or mass flow rate. The initial water content of the core air 64 (the water content of the core air 64 upstream of the steam injection location) will affect the total water content in the core air 64 downstream of the steam injection location because the steam 128 adds water to the core air 64 in addition to the initial water content. For the same position of the steam control valve 112, ambient air with a high water vapor content will result in a higher water content and mass flow rate of the core air 64 than ambient air with a low water vapor content.

[0062] The turbine engine 10, and more specifically, the controller 130 discussed herein, takes into account the water content of a volume of air 58, or more specifically, the core air 64, upstream of the steam injection location and accordingly adjusts the amount of steam 128 flowing into the core air flow path 33 to achieve a desired water-to-air ratio and mass flow rate. More specifically, the controller 130 determines the water content of the core air 64 upstream of the steam injection location, as will be discussed further below, and changes the position of the steam flow control valve 112 based on the water content of the core air 64 upstream of the steam injection location.

[0063] The controller 130 may receive inputs from which the controller 130 may determine the water content of the core air 64 upstream of the steam injection location. The controller 130 may be coupled to one or more sensors 136. The sensors 136 may be located on the aircraft, and more specifically, on the turbine engine 10, to detect parameters indicative of the water content of the core air 64 upstream of the steam injection location. These sensors 136 are described as being located at a portion of the turbine engine 10, and more specifically, in the flow path of the air measured by the sensors 136, but the sensors 136 may be located at any location where the measured parameter can be measured and detected. Figure 2 As shown, controller 130 is coupled to plurality of sensors 136 to receive inputs therefrom.

[0064] A plurality of sensors 136 may include a plurality of temperature sensors. The parameter indicating the water content of the core air 64 upstream of the steam injection position may be temperature. Each temperature sensor is located in the turbine engine 10 to detect the temperature of the air flowing through the turbine engine 10. As described above, when the core air 64 flows through the core air flow path 33, the core air 64 is compressed. As the core air 64 is compressed (pressure increases), the temperature of the core air 64 also increases. The inventor has found that this temperature increase is affected by the water vapor content of the core air 64. For the same pressure increase, the temperature increase of the core air 64 with a high water content is less than the temperature increase of the core air 64 with a low water content. The temperature sensor may be positioned to measure the temperature rise on at least a portion of the compressor. For example, one of the plurality of temperature sensors may be a core inlet temperature sensor 142 located at the core inlet 20, and more specifically, located at the core inlet 20. The core inlet 20 is also positioned near or at the inlet of the LPC 22, and the core inlet temperature sensor 142 is also a compressor inlet sensor, and more specifically, an LPC inlet temperature sensor. Another of the multiple temperature sensors is an intermediate compressor temperature sensor 144 located between the LPC 22 and the HPC 24 in the core air flow path 33. The intermediate compressor temperature sensor 144 can be positioned near or at the outlet of the LPC 22, and can be a compressor outlet sensor, and more specifically, an LPC outlet temperature sensor. With the core inlet temperature sensor 142 and the intermediate compressor temperature sensor 144 positioned in this manner, the core inlet temperature sensor 142 and the intermediate compressor temperature sensor 144 are positioned to measure the temperature increase across the LPC 22. The controller 130 receives input from each of the core inlet temperature sensor 142 and the intermediate compressor temperature sensor 144 and then determines the moisture content of the compressed air 65 flowing through the LPC 22 based on the temperature increase from the core inlet temperature sensor 142 to the intermediate compressor temperature sensor 144 .

[0065] Similarly, the intermediate compressor temperature sensor 144 may be positioned near or at the inlet of the HPC 24 and is also a compressor inlet sensor, and more specifically, an HPC inlet temperature sensor. Another temperature sensor, the HPC outlet temperature sensor 146, is positioned near or at the outlet of the HPC 24 and is a compressor outlet sensor. With the intermediate compressor temperature sensor 144 and the HPC outlet temperature sensor 146 positioned in this manner, the intermediate compressor temperature sensor 144 and the HPC outlet temperature sensor 146 are positioned to measure the temperature increase across the HPC 24. The controller 130 receives input from each of the intermediate compressor temperature sensor 144 and the HPC outlet temperature sensor 146, and then the controller 130 determines the moisture content of the compressed air 65 flowing through the HPC 24 based on the temperature increase from the intermediate compressor temperature sensor 144 to the HPC outlet temperature sensor 146.

[0066] Similarly, the fan 38 also produces a pressure increase, and for the purposes of this discussion, the fan 38 is a compressor. A temperature sensor in a plurality of temperature sensors may be positioned to measure a temperature increase on the fan 38, similar to the temperature increase on the LPC 22 and the HPC 24. For example, a fan inlet temperature sensor 148 may be positioned near or at the engine inlet 60, such as on an inner surface of the nacelle 50. The fan inlet temperature sensor 148 may be a compressor inlet sensor, and more specifically, a fan inlet temperature sensor. The fan inlet temperature sensor 148 may be used in conjunction with another temperature sensor, such as a core inlet temperature sensor 142 positioned at the outlet of the fan 38, and the core inlet temperature sensor 142 may be a compressor outlet sensor, and more specifically, a fan outlet temperature sensor. The controller 130 receives input from each of the fan inlet temperature sensor 148 and the core inlet temperature sensor 142, and then determines the moisture content of the volume of air 58 flowing into the turbine engine 10, and more specifically, the fan 38, based on the temperature increase from the fan inlet temperature sensor 148 to the core inlet temperature sensor 142. Although described with reference to the core inlet temperature sensor 142, the fan outlet temperature sensor may be located elsewhere downstream of the fan 38 to measure the pressure increase across the fan 38, such as within the bypass airflow passage 56 to measure the temperature of the bypass air 62.

[0067] Although described above as measuring the temperature increase on the compressor (e.g., fan 38, LPC 22, or HPC 24) to determine the water content of the core air 64 upstream of the steam injection location, the temperature sensor can be positioned to measure the temperature increase on any portion of the core air flow path 33. For example, the LPC 22 and HPC 24 may include multiple stages, and the temperature sensor can be positioned to measure the temperature increase on one or more stages of the LPC 22 or HPC 24. The relationship between the temperature increase and the water vapor content of the air based on the temperature increase may vary depending on the specific engine design. For example, as part of an engine development program, the turbine engine 10 may conduct a series of tests and map the compressor, and empirically determine the relationship between the pressure rise, the temperature rise, and the water content of the core air 64 upstream of the steam injection location.

[0068] As described above, the temperature increase is caused by the pressure increase in the core air 64. Therefore, the plurality of sensors 136 may also include a plurality of pressure sensors positioned to measure the pressure increase on the compressor or a portion thereof. The controller 130 may use the pressure increase to determine the water content of the compressed air 65 upstream of the steam injection location, for example in combination with the temperature sensor discussed above. Therefore, the plurality of pressure sensors may be positioned similarly to the temperature sensor discussed above, but measure pressure instead of temperature. More specifically, the plurality of sensors 136 may include (i) a core inlet pressure sensor 152 positioned similarly to the core inlet temperature sensor 142, (ii) an intermediate compressor pressure sensor 154 positioned similarly to the intermediate compressor temperature sensor 144, (iii) an HPC outlet pressure sensor 156 positioned similarly to the HPC outlet temperature sensor 146, and (iv) a fan inlet pressure sensor 158 positioned similarly to the fan inlet temperature sensor 148.

[0069] The pressure increase produced by the compressor discussed herein may be based on the rotational speed of the compressor blades. Therefore, the plurality of sensors 136 may also include one or more speed sensors positioned to detect the rotational speed of the compressor on which the temperature increase is being measured. For example, the compressor discussed herein is driven (rotated) by a shaft, and a speed sensor may be used to detect the rotational speed of the shaft. For example, the HP speed sensor 162 may be positioned to measure the rotational speed of the HP shaft 34, and the LP speed sensor 164 may be positioned to measure the rotational speed of the LP shaft 36. The controller is configured to receive input from a speed sensor (e.g., the HP speed sensor 162 or the LP speed sensor 164), and use the input from the speed sensor when determining the water content of the compressed air 65 upstream of the steam injection location.

[0070] Figure 31 is a schematic diagram of a turbine engine 10 having a steam system 100b according to another embodiment of the present disclosure. For clarity of other steam systems discussed herein, the steam system 100b of this embodiment will be referred to as the second steam system 100b. The second steam system 100b can be used as Figure 1 The steam system 100 in the turbine engine 10 is shown. The second steam system 100b is similar to the one described above with reference to Figure 2 The first steam system 100a discussed above. The same reference numerals will be used for the components of the second steam system 100b that are the same or similar to the components of the first steam system 100a discussed above. The above description of these components also applies to the present embodiment, and the detailed description of these components is omitted here.

[0071] exist Figure 2 In the embodiment shown, a steam injection zone is depicted, but in Figure 3 In the illustrated embodiment, multiple steam injection zones, including a main steam injection zone 220 and a secondary steam injection zone 230, are depicted for injecting steam 128 into the core air flow path 33. Within each zone, multiple steam injectors (i.e., main steam injectors 222 or secondary steam injectors 232) may be used to inject steam 128 into the zone. Various suitable steam injectors may be used, including, for example, nozzles and orifices formed in various components and fluidly coupled to steam lines that transport steam 128 from the steam turbine 110. Thus, the second steam system 100b includes two or more groups of steam injectors, including a group of main steam injectors 222 and a group of secondary steam injectors 224.

[0072] The main steam injection zone 220 is positioned to inject at least a portion of the steam 128 into the main air. The steam 128 may be injected into the combustor 26, such as into the combustion chamber, and more specifically, into the main combustion zone. Figure 3 As shown, the main steam injection zone 220 is the main combustion zone. When steam 128 is injected into the main combustion zone, the main steam injector 222 can be the mixer assembly discussed above. Additionally, or alternatively, the main steam injection zone 220 can be a steam injection zone upstream of the combustor 26 and downstream of the HPC 24.

[0073] The secondary steam injection zone 230 is positioned to inject a portion of the steam 128 into the core air flow path 33 at a location other than the primary steam injection zone 220. The secondary steam injection zone 230 may be a downstream steam injection zone positioned to inject steam 128 downstream of the primary steam injection zone 220 and / or the primary combustion zone. Figure 3In the illustrated embodiment, the secondary steam injection zone 230 is a portion of the combustor downstream of the primary combustion zone, but the secondary steam injection zone 230 may be located at other downstream locations, such as the HPT 28 (e.g., HPT stator vanes 68 and / or HPT rotor blades 70) or the LPT 30 (e.g., LPT stator vanes 72 or LPT rotor blades 74). Although Figure 3 Only one main steam injection zone 220 is shown in FIG. 1 , but the second steam system 100 b may include a plurality of main steam injection zones 220 .

[0074] As discussed above, steam 128 can be injected into the core air flow path 33 in a range of 20% to 50% of the mass flow rate through the core air flow path 33. In order to achieve the benefits of waste heat recovery discussed herein, this amount of steam 128 is beneficial when the steam 128 (water vapor) flows through the turbine section 27, and more specifically, flows through the HPT 28 and the LPT 30. In addition, the amount of steam required may vary depending on operating conditions throughout the flight of the aircraft. Introducing the amount of steam discussed above so that all the steam 128 flows through the main combustion zone may cause problems for flame stability and flame dynamics in the combustion chamber. Therefore, the steam 128 injected at the main steam injection zone 220 can be controlled to maintain the steam flow rate through the main combustion zone at a desired level. Since the flow rate of the steam injected at the main steam injection zone 220 is limited to achieve the steam level required for flame stability, the remainder of the steam 128 is injected into the core air flow path 33 at one or more main steam injection zones 220.

[0075] Each steam injection zone may include a steam flow control valve operable to control the flow of steam 128 into the corresponding zone. More specifically, the primary steam injection zone 220 includes a primary steam flow control valve 224 to control the flow of steam 128 into the primary steam injection zone 220, and the secondary steam injection zone 230 includes a secondary steam flow control valve 234 to control the flow of steam 128 into the secondary steam injection zone 230. Any suitable flow control valve may be used for the primary steam flow control valve 224 and the secondary steam flow control valve 234. Figure 2 The discussion of suitable flow control valves for the steam control valve 112 also applies to the main steam flow control valve 224 and the secondary steam flow control valve 234. The controller 130 may be communicatively and operably coupled to each of the main steam flow control valve 224 and the secondary steam flow control valve 234 to control the main steam flow control valve 224 and the secondary steam flow control valve 234 in a manner similar to the operation of the steam control valve 112 discussed above.

[0076] The second steam system 100b may also include one or more bypass flow paths. In the event that the steam 128 is limited based on the water content of the compressed air 65 downstream of the steam injection zone, some of the steam 128 produced by the second steam system 100b may be diverted (redirected) from the core air flow path 33. Thus, the second steam system 100b may include a bypass flow path 240 that is selectively operable to redirect the steam 128 and bypass at least the burner 26. For example, Figure 3 As shown, the second steam system 100b includes a steam bypass flow path 240 that bypasses the combustor 26. The steam bypass flow path 240 includes a steam bypass line 242 that is fluidly connected to a steam line of steam 128 downstream of the steam turbine 110 and upstream of the combustor 26. The steam bypass flow path 240 includes a steam bypass valve 244 located in the steam bypass line 242. The steam bypass valve 244 is operable to open and direct the steam 128 through the steam bypass line 242, bypassing the combustor 26. The controller 130 is operably coupled to the steam bypass valve 244 to open the steam bypass valve 224, thereby bypassing the combustor 26 and directing the steam through the steam bypass line 242. The controller 130 can operate the steam bypass valve 244 based on the water content of the compressed air 65 upstream of the steam injection location in a manner similar to the operation of the steam control valve 112 discussed above. Steam bypass valve 244 may be any suitable valve, including an isolation valve that is movable between an open position and a closed position.

[0077] The steam bypass line 242 can be fluidly connected to various locations within the second steam system 100b to bypass the burner 26. For example, the steam bypass line 242 can be fluidly connected to the condenser 104 or a location upstream of the condenser 104, allowing the steam 128 to flow and mix with the combustion gases 66. Therefore, the steam 128 flowing through the steam bypass line 242 can be recaptured by the condenser 104 and circulated in the second steam system 100b. Bypassing the steam 128 into the condenser 104 instead of the exhaust nozzle (e.g., the fan bypass nozzle 76) can minimize the formation of the wake. The steam 128 can be discharged outside the machine instead of being recaptured, for example by being fluidly connected to the exhaust port. The exhaust port can be fluidly connected to the bypass airflow channel 56 or the fan bypass nozzle 76. In this way, the steam 128 can be discharged into the bypass air 62, for example, upstream of the condenser 104 or downstream of the condenser 104. In some embodiments, the steam 128 can be selectively discharged or recaptured. A selector valve 246 may be positioned in the steam bypass line 242 to fluidly couple the steam bypass line 241 to the outlet discussed above. Any suitable first selector valve 246 may be used, including a three-way valve.

[0078] Figure 4 1 is a schematic diagram of a turbine engine 10 having a steam system 100c according to another embodiment of the present disclosure. For clarity of other steam systems discussed herein, the steam system 100c of this embodiment will be referred to as a third steam system 100c. The third steam system 100c can be used as Figure 1 The steam system 100 in the turbine engine 10 is shown. The third steam system 100c is similar to the above reference Figure 3 The same reference numerals will be used for components of the third steam system 100c that are the same or similar to the components of the second steam system 100b discussed above. The above description of these components also applies to the present embodiment, and detailed descriptions of these components are omitted here.

[0079] In the second steam system 100b, the bypass flow path 240 includes a selector valve 246 positioned in the steam bypass line 242 to fluidly couple the steam bypass line 241 to the outlet discussed above. Figure 4 The third steam system 100b shown in FIG. 1 includes two bypass lines (ie, two steam bypass flow paths), a first steam bypass line 252 and a second steam bypass line 254, each of which is fluidly coupled to one of the outlets discussed above. Figure 4 As shown, a first steam bypass line 252 is fluidly coupled to the fan bypass nozzle 76 and a second steam bypass line 254 is fluidly coupled to the condenser 104. Each bypass line includes a steam bypass valve that is operable in a manner similar to the steam bypass valve 244 discussed above. More specifically, the first steam bypass valve 256 is operable to open and direct the steam 128 through the first steam bypass line 252 to the fan bypass nozzle 76, bypassing the combustor 26, and the second steam bypass valve 258 is operable to open and direct the steam 128 through the second steam bypass line 254 to the condenser 104, bypassing the combustor 26.

[0080] Figure 5 It shows the control Figures 2 to 4 100b. A flow chart of a method for a steam system as shown in any of the figures. Other details of the method described above with respect to the operation of the above components and the description are described above. The method can be implemented by a controller 130, and the controller 130 can be configured to perform the steps of the method discussed below. Although the following discussion relates to the second steam system 100b, the discussion also applies to the first steam system 100a and the third steam system 100c.

[0081] The method may begin by measuring (or detecting) a parameter indicative of the moisture content of the core air 64 upstream of the steam injection location using, for example, one or more of the plurality of sensors 136 in step S302. More specifically, the temperature of a volume of air 58 and / or the core air 64 may be measured at one or more of the locations discussed above using one or more temperature sensors, such as the core inlet temperature sensor 142, the intermediate compressor temperature sensor 144, the HPC outlet temperature sensor 146, and the fan inlet temperature sensor 148. Similarly, the pressure of a volume of air 58 and / or the core air 64 may be measured at one or more of the locations discussed above using one or more pressure sensors, such as the core inlet pressure sensor 152, the intermediate compressor pressure sensor 154, the HPC outlet pressure sensor 156, and the fan inlet pressure sensor 158. Additionally or alternatively, the speed of the compressor (e.g., the fan 38, the LPC 22, and / or the HPC 24) may be measured using, for example, the HP speed sensor 162 and / or the LP speed sensor 164.

[0082] Then, in step S310, the water vapor content (e.g., water to air ratio) is calculated or otherwise determined using, for example, a temperature rise method based on temperature differences and pressure rise across the compressor (e.g., fan 38, LPC 22, and / or HPC 24). In step S315, one or more steam control valves, such as the main steam flow control valve 224, the secondary steam flow control valve 234, or both, are used to adjust the amount of steam injected into the core air flow path 33. Then, in step S320, the excess steam is diverted by opening the main steam flow control valve 224 and directing the steam through the steam bypass flow path 240, and more specifically, through the steam bypass line 242.

[0083] For example, when the aircraft (turbine engine 10) is operated under humid atmospheric conditions (e.g., rain, hail, or clouds), the air flowing into the turbine engine 10 and the core air 64 flowing into the core air flow path 33 contain moisture. The embodiments discussed herein control the amount of steam 128 injected into the core air 64 based on the moisture content of the incoming core air, and the amount of steam 128 injected into the core air 64 by the steam system 100 can be reduced when the turbine engine 10 is operated under humid atmospheric conditions compared to other atmospheric conditions with lower moisture content. Controlling the steam 128 in this manner using the system described herein maintains a stable flame in the combustor and provides ideal flame dynamics during fuel combustion, particularly for highly reactive fuels such as diatomic hydrogen.

[0084] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0085] A turbine engine for an aircraft, the turbine engine comprising a turbocharger, a fan shaft coupled to the turbocharger to rotate a fan shaft, and a steam system. The turbocharger comprises a core air flow path for core air to flow therethrough, a burner, an engine shaft, and a turbine. The burner is located in the core air flow path to receive compressed air and is fluidly coupled to a fuel source to receive fuel. The fuel is injected into the burner to mix with the compressed air to produce a fuel and air mixture. The fuel and air mixture is burned in a primary combustion zone of the burner to produce combustion gases. The turbine is located downstream of the burner to receive the combustion gases and rotate the turbine. The turbine is coupled to the engine shaft to rotate the engine shaft when the turbine rotates. The steam system extracts water from the combustion gases and vaporizes the water to produce steam. The steam system is fluidly coupled to the core air flow path to inject the steam into the core air flow path at a steam injection position, thereby adding mass flow to the core air. The steam system includes a steam flow control valve operable to control the flow of the steam entering the core air flow path. A sensor is located on the turbine engine for detecting a parameter indicative of a core air moisture content, the core air moisture content being the moisture content of the core air upstream of the steam injection location. A controller is operably coupled to the steam flow control valve to control a position of the steam flow control valve and an amount of the steam injected into the core air flow path at the steam injection location. The controller is configured to receive input from the sensor, determine the core air moisture content based on the input received from the sensor, and change the position of the steam flow control valve and the amount of the steam injected into the core air flow path at the steam injection location based on the core air moisture content.

[0086] A turbine engine according to the preceding clause, wherein the sensor is one of a temperature sensor or a pressure sensor.

[0087] A turbine engine as claimed in any preceding clause, wherein the core air flow path comprises a core inlet, the sensor being located at the core inlet to detect the parameter indicative of the water content of the core air in the core inlet.

[0088] A turbine engine according to any preceding clause, further comprising a nacelle circumferentially surrounding the fan, the nacelle defining a fan inlet for receiving a volume of air, the sensor being located at the fan inlet to detect in the volume of air the parameter indicative of the core air moisture content.

[0089] Turbine engine according to the preceding clause, said sensor being located on said nacelle in said fan inlet.

[0090] A turbine engine according to any preceding clause, wherein the steam flow control valve is a main steam flow control valve capable of operating to control the flow of the steam entering a main steam injection zone, the main steam injection zone being a steam injection zone located in the core air flow path, so that the steam injected into the main steam injection zone flows into the main combustion zone.

[0091] A turbine engine as described in any preceding clause, wherein the primary steam injection zone is the primary combustion zone.

[0092] A turbine engine according to any preceding clause, wherein the turbocharger engine includes a compressor located in the core air flow path and upstream of the combustor to compress the core air to produce the compressed air, and the sensor is a compressor discharge sensor located at the outlet of the compressor or downstream thereof to detect in the compressed air the parameter indicative of the water content of the core air.

[0093] A turbine engine according to the preceding clause, wherein the turbocharged engine includes a shaft coupled to the compressor to rotate the compressor and a speed sensor positioned to detect a rotational speed of the shaft, the controller being configured to receive input from the speed sensor and to use the input from the speed sensor in determining the core air water content.

[0094] A turbine engine according to any preceding clause, wherein the compressor discharge sensor is one of a plurality of sensors, each of the plurality of sensors being located on the turbine engine to detect a parameter indicative of the core air water content, another of the plurality of sensors being a compressor inlet sensor located at or upstream of an inlet of the compressor to detect the parameter indicative of the core air water content.

[0095] A turbine engine according to the preceding clause, wherein each of the compressor inlet sensor and the compressor discharge sensor is a temperature sensor, and the controller is configured to determine the core air water content based on a temperature increase from the compressor inlet sensor to the compressor discharge sensor.

[0096] A turbine engine as in any preceding clause, wherein each of the compressor inlet sensor and the compressor discharge sensor is a pressure sensor, and the controller is configured to determine the core air water content using a pressure increase from the compressor inlet sensor to the compressor discharge sensor.

[0097] A turbine engine according to any preceding clause, wherein the steam system includes a steam bypass flow path, the steam bypass flow path being selectively operable to redirect at least a portion of the steam to bypass the core air flow path, and the controller being configured to redirect a portion of the steam through the steam bypass flow path based on the core air water content.

[0098] A turbine engine as recited in the preceding clause, wherein said steam bypass flow path is fluidly connected to an exhaust port for selectively exhausting said steam.

[0099] A turbine engine according to any preceding clause, further comprising a bypass airflow passage for bypass air, said steam bypass flow path being fluidly connected to said bypass airflow passage for selectively directing a flow of steam into said bypass airflow passage.

[0100] A turbine engine as in any preceding clause, wherein the steam system comprises a boiler located downstream of the combustor, the boiler receiving water and fluidly connected to the combustor to receive the combustion gases and boil the water to generate the steam.

[0101] The turbine engine according to the preceding clause, further comprising a condenser located downstream of said boiler to condense water from said combustion gases and produce an exhaust-water mixture.

[0102] According to the turbine engine of the preceding clause, the steam bypass flow path is fluidly connected to the condenser to selectively direct the flow of steam into the condenser.

[0103] A turbine engine as recited in any preceding clause, wherein the steam bypass flow path includes a valve operable to selectively redirect the steam to at least one of the condenser or the exhaust.

[0104] A turbine engine as in any preceding clause, wherein the steam bypass flow path is fluidly connected to the steam system at a location downstream of the boiler and upstream of the core air flow path.

[0105] A turbine engine as in any preceding clause, wherein the bypass flow path is a steam bypass flow path fluidly connected to the steam system at a location downstream of the boiler and upstream of the combustor.

[0106] A turbine engine according to any preceding clause, further comprising a bypass airflow passage for bypass air, said water bypass flow path being fluidly connected to said bypass airflow passage for selectively directing a flow of steam into said bypass airflow passage.

[0107] A turbine engine according to any preceding clause, wherein the bypass airflow passage comprises a bypass airflow exhaust nozzle for exhausting the bypass air, the steam bypass flow path being fluidly connected to the bypass airflow exhaust nozzle.

[0108] A turbine engine as claimed in any preceding clause, wherein the steam bypass flow path is fluidly connected to the bypass air flow passage at a location downstream of the condenser.

[0109] A turbine engine as claimed in any preceding clause, wherein the steam bypass flow path is fluidly connected to the bypass air flow passage at a location upstream of the condenser.

[0110] A turbine engine according to any preceding clause, wherein the steam system includes a steam turbine fluidly coupled to the boiler to receive the steam from the boiler and rotate the steam turbine, the steam turbine coupled to the engine shaft to rotate the engine shaft when the steam turbine rotates.

[0111] A turbine engine according to the preceding clause, wherein said steam bypass flow path is fluidly connected to said steam system at a location downstream of said steam turbine.

[0112] A turbine engine according to the preceding clause, wherein said turbocharger engine comprises a compressor positioned in said core air flow path, upstream of said combustor, to compress core air to produce said compressed air.

[0113] A turbine engine as described in any preceding clause, wherein the turbocharger engine includes a combined fuel and steam nozzle assembly to inject both the steam and the fuel into the primary combustion zone.

[0114] A turbine engine according to any preceding clause, wherein the turbine is a high pressure turbine.

[0115] A turbine engine according to any preceding clause, wherein the turbine is a low pressure turbine.

[0116] A turbine engine as claimed in any preceding clause, wherein the turbocharger engine comprises a high pressure compressor positioned in the core air flow path upstream of the combustor to produce the compressed air.

[0117] A turbine engine according to any preceding clause, wherein the engine shaft is a high pressure shaft.

[0118] A turbine engine as described in any preceding clause, wherein the high pressure compressor is driven by the high pressure shaft to compress the core air flowing through the core air flow path and produce the compressed air.

[0119] A turbine engine as claimed in any preceding clause, wherein the turbocharged engine comprises a low pressure compressor positioned in the core air flow path upstream of the high pressure compressor to produce the compressed air.

[0120] A turbine engine as claimed in any preceding clause, wherein the turbocharged engine comprises a low pressure turbine positioned in the core air flow path downstream of the high pressure turbine to receive the combustion gases and to rotate the turbine.

[0121] A turbine engine according to any preceding clause, wherein the turbocharger engine comprises a low pressure shaft, the low pressure turbine being coupled to the low pressure shaft to rotate the low pressure shaft when the low pressure turbine rotates.

[0122] A turbine engine as claimed in any preceding clause, wherein the turbocharger engine comprises a compressor positioned in the core air flow path upstream of the combustor to compress core air to produce the compressed air.

[0123] A turbine engine according to the preceding clause, wherein said compressor is driven by said high pressure shaft to compress said core air flowing through said core air flow path and produce said compressed air.

[0124] A turbine engine according to any preceding clause, wherein the turbine is a low pressure turbine and a steam injection zone is located in the low pressure turbine.

[0125] The turbine engine according to the preceding clause, wherein the low-pressure turbine comprises a turbine rotor comprising a plurality of rotor blades, and wherein the steam injection region is the plurality of rotor blades.

[0126] A turbine engine according to any preceding clause, wherein the engine shaft is a low pressure shaft and the turbine is a low pressure turbine.

[0127] A turbine engine as claimed in any preceding clause, wherein the fan shaft is coupled to the low pressure shaft to be driven by the low pressure shaft.

[0128] A turbine engine according to any preceding clause, further comprising a nacelle circumferentially surrounding said fan.

[0129] A turbine engine as described in any preceding clause, wherein the fan comprises a plurality of fan blades that rotate to produce a volume of air.

[0130] A turbine engine according to the preceding clause, wherein the nacelle defines a bypass airflow passage between the nacelle and the turbocharger engine, the volume of air from the fan being diverted and flowing into the bypass airflow passage as bypass air and into the core air flow path as core air.

[0131] A turbine engine according to any preceding clause, wherein the steam system includes a boiler located downstream of the combustor, the boiler receiving the extracted water and being fluidly connected to the combustor to receive the combustion gases and boil the water to generate the steam.

[0132] The turbine engine according to the preceding clause, wherein the steam system comprises a steam turbine. The steam turbine is fluidly coupled to the boiler to receive the steam from the boiler and to rotate the steam turbine.

[0133] A turbine engine according to the preceding clause, wherein the steam turbine is coupled to the engine shaft to rotate the engine shaft when the steam turbine rotates.

[0134] A turbine engine as claimed in any preceding clause, wherein the steam system comprises a condenser downstream of the turbine for receiving the combustion gases and condensing the water therefrom.

[0135] A turbine engine according to the preceding clause, wherein said condenser is located downstream of said boiler.

[0136] A turbine engine as claimed in any preceding clause, wherein the condenser is located in the bypass air flow passage for bypass air to cool the combustion gases and condense the water therefrom.

[0137] A turbine engine as claimed in any preceding clause, wherein the steam system comprises a water separator located downstream of the condenser, the water separator separating the water from the exhaust-water mixture.

[0138] A turbine engine as claimed in any preceding clause, wherein the water separator is fluidly connected to the boiler to provide the water to the boiler.

[0139] A turbine engine according to the preceding clause, wherein the water separator is a cyclone separator.

[0140] A turbine engine as claimed in any preceding clause, further comprising a water pump in fluid communication with the water separator and with the boiler to direct a flow of water from the water separator into the boiler.

[0141] A method of operating a turbine engine for an aircraft having a steam system. The method includes determining a core air water content, the core air water content being the water content of air in a core air flow path. The method also includes injecting fuel into a combustor positioned in the core air flow path to receive compressed air, mixing the fuel with the compressed air to produce a fuel and air mixture, and combusting the fuel and air mixture in a primary combustion zone of the combustor to produce combustion gases. The method also includes extracting water from the combustion gases, vaporizing the water to produce steam, and injecting the steam into the core air flow path at a steam injection location, thereby adding a mass flow rate to the core air. The method further includes determining an amount of the steam injected into the core air flow path at the steam injection location based on the core air water content.

[0142] A method as described in the preceding clause, wherein determining the core air moisture content comprises measuring the moisture content of a volume of air flowing into a fan inlet.

[0143] A method as in any preceding clause, wherein determining the core air moisture content comprises measuring the moisture content of a volume of air flowing into a core inlet.

[0144] A method as in any preceding clause, wherein determining the core air moisture content comprises measuring the moisture content of core air flowing through the core air flow path.

[0145] A method as in any preceding clause, wherein determining the core air water content comprises measuring the water content of the compressed air in a compressor.

[0146] A method as in any preceding clause, wherein determining the core air moisture content comprises measuring a temperature difference between air flowing into an inlet of a compressor and air discharged from the compressor.

[0147] A method according to any preceding clause, wherein the compressor is a compressor of any turbine engine according to any preceding clause.

[0148] A method as in any preceding clause, wherein determining the core air moisture content comprises measuring a pressure increase between air flowing into an inlet of a compressor and air discharged from the compressor.

[0149] A method as in any preceding clause, wherein determining the core air water content comprises measuring a rotational speed of a compressor.

[0150] A method according to the preceding clause, wherein the compressor is a compressor of a turbine engine according to any preceding clause.

[0151] A method according to any preceding clause, further comprising operating a turbine engine according to any preceding clause.

[0152] A turbine engine as claimed in any preceding clause, further comprising a controller configured to perform a method as claimed in any preceding clause.

[0153] Although the above description is directed to certain embodiments, other variations and modifications will be apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, features described in conjunction with one embodiment may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A turbine engine for an aircraft, characterized in that: The turbine engine comprises: A turbocharged engine, the turbocharged engine comprising: a core air flow path for core air to flow therethrough; a combustor located in the core air flow path to receive compressed air and fluidly coupled to a fuel source to receive fuel, the fuel being injected into the combustor to mix with the compressed air to produce a fuel and air mixture that is combusted in a primary combustion zone of the combustor to produce combustion gases; engine shaft; and a turbine located downstream of the combustor to receive the combustion gases and rotate the turbine, the turbine being coupled to the engine shaft to rotate the engine shaft when the turbine rotates; a fan having a fan shaft coupled to the turbocharger engine for rotation of the fan shaft; a steam system that extracts water from the combustion gases and vaporizes the water to produce steam, the steam system being fluidly coupled to the core air flow path to inject the steam into the core air flow path at a steam injection location to add a mass flow to the core air, the steam system comprising a steam flow control valve operable to control the flow of the steam entering the core air flow path; a sensor located on the turbine engine for detecting a parameter indicative of a core air moisture content, the core air moisture content being the moisture content of the core air upstream of the steam injection location; and a controller operably connected to the steam flow control valve to control a position of the steam flow control valve and an amount of the steam injected into the core air flow path at the steam injection position, wherein the controller is configured to receive input from the sensor, determine the core air moisture content based on the input received from the sensor, and change the position of the steam flow control valve and the amount of the steam injected into the core air flow path at the steam injection position based on the core air moisture content.

2. The turbine engine according to claim 1, characterized in that The sensor is a temperature sensor or a pressure sensor.

3. The turbine engine according to claim 1, characterized in that: The core air flow path includes a core inlet, and the sensor is located at the core inlet to detect the parameter indicative of the moisture content of the core air in the core inlet.

4. The turbine engine according to claim 1, characterized in that: Further included is a nacelle circumferentially surrounding the fan, the nacelle defining a fan inlet for a volume of air, the sensor being located at the fan inlet to detect the parameter indicative of the moisture content of the core air in the volume of air.

5. The turbine engine according to claim 4, characterized in that Wherein the sensor is located on the nacelle, in the fan inlet.

6. The turbine engine according to claim 1, characterized in that The steam flow control valve is a main steam flow control valve that can be operated to control the flow of the steam entering the main steam injection zone, and the main steam injection zone is a steam injection zone located in the core air flow path, so that the steam injected into the main steam injection zone flows into the main combustion zone.

7. The turbine engine according to claim 6, characterized in that Wherein the main steam injection zone is the main combustion zone.

8. The turbine engine according to claim 1, characterized in that The turbocharged engine comprises a compressor located in the core air flow path and upstream of the combustor to compress the core air to produce the compressed air, and the sensor is a compressor discharge sensor located at the outlet of the compressor or downstream thereof to detect the parameter indicating the water content of the core air in the compressed air.

9. The turbine engine according to claim 8, characterized in that Wherein the turbocharged engine includes a shaft coupled to the compressor to rotate the compressor and a speed sensor positioned to detect a rotational speed of the shaft, the controller being configured to receive input from the speed sensor and to use the input from the speed sensor in determining the core air water content.

10. The turbine engine according to claim 8, characterized in that The compressor discharge sensor is one of a plurality of sensors, each of which is located on the turbine engine to detect a parameter indicative of the core air water content, and another of the plurality of sensors is a compressor inlet sensor located at or upstream of the inlet of the compressor to detect the parameter indicative of the core air water content.

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